Abstract
A numerical procedure is presented for computing the aerodynamic flowfield about airfoils using the twodimensional, full-potential equation. A strongly implicit approximate factorization algorithm is employed which may be applied either as a relaxation procedure for steady flow problems, or as an accurate noniterative timemarching procedure for unsteady flows. A body-fitted coordinate system which follows the airfoil motion during unsteady computations is used to permit exact application of the appropriate boundary conditions on the instantaneous airfoil surface. Numerical results are presented for steady, unsteady, subsonic, and transonic flows about several different airfoil shapes.
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